前体压缩对斜爆轰发动机推力性能影响研究

doi:10.12382/bgxb.2024.0171

摘要/Abstract

摘要：

为了探明前体压缩方式及压缩程度对斜爆轰发动机推力性能的影响规律,针对马赫数10、海拔35km的飞行工况,采用理论分析的手段,研究1道、2道和3道斜激波以及压缩角度对氢气-空气斜爆轰发动机推力性能的影响。研究结果显示,压缩级数的增加能够显著提升斜爆轰发动机的推力性能;在压缩角度2°~24°范围内,燃料比冲随着1级压缩角度的增加呈现出先增大后减小的变化趋势,2级和3级压缩角度的增加能够持续地提升燃料比冲,并延迟推力性能极值点的出现。通过分析进气压缩级数对进气道出口、掺混段出口和燃烧室出口气流参数的影响,发现这一现象主要在于1级楔面压缩角度的增加导致进气道出口气流温度快速上升,限制了爆轰燃烧的增压能力,而多级压缩能够获得更高的燃烧产物压力和速度,从而提升推力性能并降低总压损失。

关键词: 斜爆轰发动机, 前体压缩, 燃气压力, 燃气速度, 比冲

Abstract:

The influences of forebody compression methods and compression levels on the thrust performance of oblique detonation engine (ODE) are studied.The effects of 1-,2-,and 3-stage oblique shocks and compression angles on the thrust performance of hydrogen-air ODE under flight conditions of Mach number 10 and altitude 35km are examined through theoretical analysis.The results indicate a significant enhancement in thrust performance with an increase in the number of compression stages.Within the range of compression angles from 2° to 24°,the fuel specific impulse exhibits an initial increase followed by a decrease with the increase in the compression angle of the 1st stage,while the increases in the angles of the 2nd and 3rd compression lead to a continuous improvement in fuel specific impulse,thus delaying the appearance of peak thrust performance.Analysis of the impact of inlet compression stages on the total pressure at the outlet of inlet duct,the exit of mixing section,and the exit of combustion chamber reveals that the increase in the compression angle of the 1st stage wedge leads to a rapid rise in the outlet airflow temperature of inlet duct,limiting the pressure-gain capability of detonation combustion.Conversely,the multi-stage compression achieves higher combustion product pressure and velocity,thereby enhancing the thrust performance and reducing the total pressure loss.

Key words: oblique detonation engine, forebody compression, combustion pressure, combustion velocity, specific impulse

郗雪辰, 王安琪, 牛淑贞, 杨鹏飞. 前体压缩对斜爆轰发动机推力性能影响研究[J]. 兵工学报, 2025, 46(8): 240171-.

XI Xuechen, WANG Anqi, NIU Shuzhen, YANG Pengfei. The Influence of Forebody Compression on Thrust Performance of Oblique Detonation Engine[J]. Acta Armamentarii, 2025, 46(8): 240171-.

图/表 9

图1 ODE及进气压缩方式示意图

Fig.1 Schematics of oblique detonation engine and inlet compression methods

图2 不同进气压缩角度下的燃料比冲和推力

Fig.2 Fuel specific impulse and thrust with different inlet compression angles

图3 不同进气压缩级数下进气道出口、掺混段出口和燃烧室出口的气体总压

Fig.3 The total pressure of airflows at inlet exit,mixing section exit and the combustor exit under different levels of inlet compression

图4 不同进气压缩级数下燃烧室出口的气流压力和速度

Fig.4 Gas pressure and velocity at combustor exit for different inlet compression stages

图5 不同膨胀面积比例下喷管出口速度和压力

Fig.5 Nozzle exit velocity and pressure with different expansion area ratios

图6 不同进气压缩角度下进气道出口气体总压和燃烧室出口气体总压

Fig.6 Total pressure of inlet-compressed gas and detonation product with different inlet compression angles

图7 不同进气压缩角度下进气道出口气体温度和速度

Fig.7 Temperature and velocity of inlet-compressed gas-stream with different inlet compression angles

图8 不同进气压缩角度下爆轰燃烧产物的压力和速度

Fig.8 Pressures and velocities of detonation products at different inlet compression angles

图9 不同进气压缩角度下喷管出口速度

Fig.9 Nozzle exit velocity at different inlet compression angles

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